WO2022116652A1 - Procédé de prédiction de réponse structurale de moteur-fusée à propergol liquide à une charge d'impact - Google Patents

Procédé de prédiction de réponse structurale de moteur-fusée à propergol liquide à une charge d'impact Download PDF

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Publication number
WO2022116652A1
WO2022116652A1 PCT/CN2021/119739 CN2021119739W WO2022116652A1 WO 2022116652 A1 WO2022116652 A1 WO 2022116652A1 CN 2021119739 W CN2021119739 W CN 2021119739W WO 2022116652 A1 WO2022116652 A1 WO 2022116652A1
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Prior art keywords
engine
frame
impact load
tested
rocket engine
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PCT/CN2021/119739
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English (en)
Chinese (zh)
Inventor
李斌
陈晖�
王春民
高玉闪
杨飒
王猛
李斌潮
刑理想
韩帅
Original Assignee
西安航天动力研究所
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Priority claimed from CN202011400057.2A external-priority patent/CN112555055B/zh
Priority claimed from CN202011400048.3A external-priority patent/CN112504121B/zh
Application filed by 西安航天动力研究所 filed Critical 西安航天动力研究所
Priority to EP21899686.6A priority Critical patent/EP4257818A1/fr
Publication of WO2022116652A1 publication Critical patent/WO2022116652A1/fr

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/002—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/81—Modelling or simulation

Definitions

  • the invention relates to a liquid rocket engine, in particular to a liquid rocket engine impact load structure response prediction method.
  • the structure will shake violently.
  • the shaking such as the water hammer caused by the valve opening and closing process, the vibration caused by the violent combustion in the combustion chamber, and the vibration caused by the harsh working environment of the turbo pump. etc.
  • the violent shaking process may damage the structural strength of the engine under the current working conditions or even higher working conditions, so it is necessary to study the prediction method of the structural response of the engine impact load. It is difficult to identify and collect the load source during the hot test run, and there will be complex coupling between them, which makes it very difficult to obtain the excitation load in the process of engine impact dynamics research.
  • the input load used in the conventional impact dynamics research process is a single acceleration load, which is difficult to meet the multi-source load excitation in the complex hot test process. Therefore, it is necessary to develop a method for predicting the structural response of the rocket engine impact load, which can carry out the multi-source load impact dynamics research of the whole machine state without using the acceleration load as the load excitation, so as to realize the structural strength of the key parts of the engine and the rocking bearing. Analytical evaluation.
  • the purpose of the invention is to solve the technical problem that the input load used in the existing liquid rocket engine impact load structural response prediction method is a single acceleration load, which is difficult to meet the multi-source load excitation situation in the complex hot test process, and provides a liquid rocket engine.
  • a liquid rocket engine impact load structural response prediction method is special in that it includes the following steps:
  • the frame of the engine is simplified as a beam structure, the part to be tested is simplified as a shell structure, the gas elbow of the engine is a solid structure, and every small pipeline of the engine is ignored, and a simplified complete engine model is obtained.
  • the latter engine model includes a frame, a gas elbow and a turbo pump that are connected in sequence from top to bottom; the middle of the gas elbow is connected to the frame, and both ends of the gas elbow are hinged to the cantilever through rocking bearings, and the two ends of the cantilever are connected. Set up nozzles separately;
  • the simplified model of the whole engine is modeled to obtain the dynamic simulation model of the engine structure, and the frame part of the simulation model is connected with the simulation model of the moving frame of the test bench;
  • the pose change data is the curve of the displacement changing with time. Three direction data of direction and tangential direction; load the pose change data as impact load to the corresponding position of the simulation model;
  • step 3 After step 3) is completed, carry out the dynamic solution of the impact structure of the engine simulation model;
  • step 4 Using the solution results obtained in step 4), analyze the structural strength of the engine part to be tested and the rocking angle characteristics of the swing bearing at the hinge, and carry out the analysis on the structural strength of the engine in the standard operating conditions and high operating conditions. effective assessment.
  • step 5 the specific steps of analyzing the structural strength of the engine part to be measured and the rocking angle characteristics of the rocking bearing at the hinge are:
  • Extract the variation curve of the structural strength of the engine to be tested with time from the simulation model analyze the influence of the maximum structural strength and the moment when the maximum structural strength occurs on the engine structure, extract the variation curve of the rocking angle of the rocking bearing with time, and analyze the maximum structural strength.
  • step 1) when modeling in step 1), the mass of the corresponding components in the simulation model is corrected according to the actual mass of each component of the engine, so that the quality is the same.
  • the part to be tested includes a turbo pump and two nozzles.
  • step 4 when the dynamic solution of the engine impact structure is performed in step 4), the set duration is added to the output result.
  • step 4 the set duration is 1s.
  • step 3 is implemented based on a high-thrust rocket engine structure attitude monitoring system, and the high-thrust rocket engine structure attitude monitoring system includes reflective markers, reflective target balls, inertial sensors, laser trackers, control collectors and at least two high-speed cameras;
  • the inertial sensor is arranged at the docking end of the engine to be tested and the docking frame of the test bench, and is used to measure the moving speed and displacement information of the docking end of the engine to be tested;
  • the reflective marking points are arranged on the to-be-measured part of the to-be-measured engine for position identification;
  • the at least two high-speed cameras are arranged around the engine to be tested, and are used to form a three-dimensional space visual measurement domain of the engine to be tested;
  • the reflective target ball is arranged on the engine to be tested, and is in the visual measurement field of the high-speed camera;
  • the laser tracker is arranged at a position away from the test platform, and is used to track the three-dimensional dynamic trajectory of the reflective target ball in real time;
  • the input end of the control collector is simultaneously connected to the output end of the inertial sensor, the laser tracker and the high-speed camera;
  • Step 3 specifically includes the following steps:
  • step 3.2) Perform reflective marker point detection and reflective target ball detection on the image data obtained in step 3.1) frame by frame, and according to the time sequence, form the engine pose information including the additional displacement of the high-speed camera itself and the displacement of the test bench docking frame;
  • step 3.3 Using the three-dimensional dynamic trajectory of the reflective target ball obtained in step 3.1), compare the position and attitude information of the reflective target ball in the engine pose information obtained in step 3.2) frame by frame to obtain the additional displacement of the high-speed camera in the frame-by-frame image data. The displacement compensates and corrects the engine pose information obtained in step 3.2);
  • step 3.4 According to the moving speed and displacement information of the docking end of the engine obtained in step 3.1), modify the results obtained in step 3.3) to obtain the position and attitude change data of the engine relative to the docking frame, which is used for the structural response evaluation of the engine impact load.
  • the pose change data described in step 3.4) is a curve of displacement changing with time, and the curve includes data of three directions of axial X, radial Y and tangential Z.
  • At least one reflective target ball is in the visual measurement field of the high-speed camera.
  • the parts to be tested are the turbo pump and two nozzles of the engine to be tested; there are two high-speed cameras with a frame rate of 1000 frames/s; and there are multiple inertial sensors.
  • the present invention has the following beneficial effects:
  • the liquid rocket engine impact load structural response prediction method provided by the present invention integrates the liquid rocket engine structural dynamics modeling technology and the multi-excitation source impact dynamic analysis method, and reasonably simplifies the liquid rocket engine complete model.
  • the existing method overcomes the dilemma of using a single acceleration load for excitation.
  • the forced displacement load applied at multiple positions is used as the excitation input to carry out the dynamic analysis of the liquid rocket engine structure.
  • the structural strength of the key parts of the engine and the rocking angle of the rocking bearing are analyzed, so as to overcome the shortcomings of the existing technology, such as harsh technical conditions, limited scope, difficult to identify the acceleration excitation source, and single load excitation, and can provide the optimization of the engine structure and the ultimate bearing capacity. Effective evaluation, and then provide effective prediction for the structural strength of the engine in the subsequent high-condition test run.
  • the liquid rocket engine impact load structural response prediction method provided by the present invention does not require acceleration load as the load input condition, and adopts the forced displacement curve (position and attitude change data) as the load input condition , which overcomes the problem that the acceleration load excitation cannot be accurately obtained in the engine hot test run.
  • the liquid rocket engine impact load structural response prediction method provided by the present invention can simultaneously apply load excitation to multiple positions of the engine, and more realistically simulate the actual working state of the engine.
  • the strength analysis of the critical position of the engine provides a more realistic reference, and provides stronger technical support for estimating the structural strength of the engine under high operating conditions.
  • the impact load loading in the prediction method of the present invention is realized based on the structural attitude monitoring system of the high-thrust high-thrust rocket engine, combined with the multi-technological fusion of high-speed photogrammetry, laser tracking measurement and inertial sensor measurement, which is the structural response of the thermal test of the power plant. measurement technology.
  • the three-dimensional visual measurement domain is formed by more than two high-speed cameras, and the displacement of the high-thrust rocket engine structure is measured in the whole field.
  • the inertial navigation measurement and laser tracking technology are used to compensate the additional displacement of the high-speed camera and the test bench due to vibration.
  • the environmental pose (engine structure vibration displacement) measurement can accurately obtain the structural response of the engine during the thermal test run; the measured structural displacement data can be used to evaluate the engine performance, and can also be directly used for the structural response simulation analysis of the engine thermal test process. and checking to predict the structural reliability of the engine.
  • the relative position and attitude data of the engine relative to the docking frame of the test bench can be calculated, and the data can be directly applied to the simulation of the structural response of the engine based on the position and attitude changes.
  • Fig. 1 is the flow chart of the liquid rocket engine impact load structure response prediction method of the present invention
  • FIG. 2 is a schematic structural diagram of a simplified complete engine model obtained in step 1 of the liquid rocket engine impact load structural response prediction method of the present invention
  • Fig. 3 is the time-varying curve of displacement as impact load in step 3 of the embodiment of the present invention.
  • Fig. 4 is the variation curve of structural strength with time in step 5 of the embodiment of the present invention, and this figure only shows the curve corresponding to the shutdown section;
  • Fig. 5 is the variation curve of the rocking angle of the rocking bearing with time in step 5 of the embodiment of the present invention.
  • FIG. 6 is a schematic structural diagram of a high-thrust rocket engine structural attitude monitoring system in an embodiment of the present invention.
  • FIG. 7 is a graph of the position and attitude change data of the engine parts to be measured at different stages obtained by the analysis of the high-thrust rocket engine structural attitude monitoring system in the embodiment of the present invention, wherein FIG. 7( a ) is the starting section, and FIG. 7( b ) is a The main stage, Figure 7(c) is the shutdown section, in each figure, A is the first part to be measured, B is the second part to be measured, and the pose change data is the curve of displacement with time, and the curve includes axial X, Data in three directions, radial Y and tangential Z.
  • 01-Docking frame 02-Reflective marking point, 03-Reflective target ball, 04-Inertial sensor, 05-Laser tracker, 06-High-speed camera, 07-Engine to be tested, 08-Control collector, 1-Frame, 2-swing bearing, 3-turbine pump, 4-nozzle, 5-gas elbow.
  • a liquid rocket engine impact load structural response prediction method establishes the engine dynamic model and multi-source load excitation loading, so as to carry out the engine impact load structural strength analysis, check the structural strength of the key parts of the engine and the bearing rocking angle. As shown in Figure 1, it includes the following steps:
  • the structure of the whole engine is simplified.
  • the frame 1 of the engine is simplified to a beam structure
  • the parts to be tested (key components, such as the turbo pump 3 and the two nozzles 4) of the engine are simplified to a shell structure
  • the gas elbow 5 of the engine is a solid structure, ignoring
  • a simplified model of the whole engine is obtained, as shown in Figure 2, including the frame 1, the gas elbow 5 and the turbo pump 3 connected in sequence from top to bottom; the middle of the gas elbow 5 is connected to the
  • the frame 1 is connected, the two ends of the gas elbow 5 are respectively hinged to the cantilever through the swing bearing 2, and the two cantilever ends are respectively provided with a nozzle 4;
  • Model the simplified engine model to obtain the engine structural dynamics simulation model. According to the actual mass of each component of the engine, the quality of the corresponding components in the simulation model is corrected to make the quality the same. Partly connected with the simulation model of the test bench moving frame;
  • the pose change data is the curve of the displacement with time.
  • the curve contains data in three directions: axial, radial and tangential; the pose change data is loaded into the corresponding position of the simulation model as an impact load (forced displacement load); the three positions to be measured are the highest points of the free end of the engine.
  • the far end, the swing amplitude is the largest during the hot test run, which can cover the swing displacement area of the rest of the engine and cover all transmission paths of the engine;
  • step 3 After step 3) is completed, carry out the dynamic solution of the impact structure of the engine simulation model; considering that the structural dynamic response of the engine will be delayed under the action of the impact load, 1 s is added to the output result when the dynamic solution of the engine impact structure is performed.
  • step 4 analyze the structural strength of the engine part to be tested and the rocking angle characteristics of the swing bearing 2 at the hinged position, and based on the analysis results, analyze the structural strength safety margin of the engine during the test run under standard operating conditions and high operating conditions. Efficient evaluation is carried out and the corresponding structural parameters of the engine are optimized.
  • step 5 the specific steps of analyzing the structural strength of the engine part to be tested and the rocking angle characteristics of the rocking bearing 2 at the hinge are as follows:
  • Fig. 4 is the variation curve of the structural strength with time, and only the curve corresponding to the shutdown section is shown in the figure;
  • Fig. 5 is the variation curve of the rocking angle of the rocking bearing 2 with time.
  • Step 3 can be implemented based on the high-thrust rocket engine structure and attitude monitoring system, as shown in Figure 6, including multiple reflective marking points 02, multiple reflective target balls 03, multiple inertial sensors 04, multiple laser trackers 05, control acquisition 08 and two high-speed cameras 06 with 1000 frames/s; the inertial sensor 07 is arranged at the butt end of the engine to be tested 07 and the docking frame 01 of the test bench.
  • a plurality of reflective marking points 02 are arranged on the part to be measured of the engine 07 to be measured (key parts of the engine, such as turbo pump and two nozzles) for position identification;
  • Each high-speed camera 06 is arranged around the engine 07 to be tested, and is calibrated before the test to form a three-dimensional space visual measurement domain of the engine 07 to be tested;
  • a plurality of reflective target balls 03 are placed on the engine 07 to be tested, and at least one reflective target is placed on the engine 07 to be tested.
  • the ball 03 is in the visual measurement field of the high-speed camera 06; the laser tracker 05 is reliably and fixedly arranged at a position away from the test bed (away from the engine), and is not affected by the vibration of the test bed, and is used for real-time tracking of the three-dimensional reflective target ball 03 Dynamic trajectory; the input end of the control collector 08 is connected to the output end of the inertial sensor 04, the laser tracker 05 and the high-speed camera 06 at the same time.
  • Step 3 is specifically implemented through the following steps:
  • step 3.1) The image data obtained in step 3.1) is subjected to the detection of reflective marking points 02 and the detection of reflective target balls 03 frame by frame, and according to the time sequence, the engine pose information including the additional displacement of the high-speed camera 06 itself and the displacement of the test bench docking frame 01 is formed;
  • step 3.3 Using the three-dimensional dynamic trajectory of the reflective target ball 03 obtained in step 3.1), compare the pose information of the reflective target ball 03 in the engine pose information obtained in step 3.2) frame by frame to obtain the additional displacement of the high-speed camera 06 in the frame-by-frame image data , using the additional displacement to compensate and correct the engine pose information obtained in step 3.2);
  • step 3.4 According to the moving speed and displacement information of the engine docking end obtained in step 3.1), modify the results obtained in step 3.3) to obtain the position and attitude change data of the engine relative to the docking frame 01.
  • the curve contains data in three directions, axial X, radial Y, and tangential Z, and is used for structural response evaluation of engine shock loads.

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Abstract

La présente invention concerne un procédé de prédiction d'une réponse structurale d'un moteur-fusée à propergol liquide à une charge d'impact. Le but de la présente invention est de résoudre le problème technique de l'état de la technique, c'est-à-dire la difficulté de répondre à une condition d'excitation par charges de multiples sources pendant un processus de mise en service à chaud complexe, du fait que les charges d'entrée utilisées sont toutes des charges à accélération unique. Est divulgué un procédé de prédiction d'une réponse structurale d'un moteur-fusée à propergol liquide à une charge d'impact. Selon la présente invention, une technique de modélisation dynamique pour toute la structure d'un moteur-fusée à propergol liquide et un procédé d'analyse dynamique pour un impact à multiples sources d'excitation sont combinés. Sur la base d'une simplification rationnelle de l'ensemble du modèle du moteur-fusée à propergol liquide, on effectue une analyse dynamique de toute la structure du moteur-fusée à propergol liquide au moyen de l'application d'une charge de déplacement forcé en de multiples emplacements servant d'entrées d'excitation et au moyen de l'analyse de la résistance structurale de parties clés du moteur et de l'angle d'oscillation d'un palier oscillant, ce qui permet une évaluation efficace pour optimiser la structure de moteur et pour une capacité optimale de palier, afin de fournir une estimation efficace de la résistance structurale du moteur lors d'une mise en service ultérieure en condition de travail intense.
PCT/CN2021/119739 2020-12-02 2021-09-23 Procédé de prédiction de réponse structurale de moteur-fusée à propergol liquide à une charge d'impact WO2022116652A1 (fr)

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EP21899686.6A EP4257818A1 (fr) 2020-12-02 2021-09-23 Procédé de prédiction de réponse structurale de moteur-fusée à propergol liquide à une charge d'impact

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Application Number Priority Date Filing Date Title
CN202011400057.2A CN112555055B (zh) 2020-12-02 2020-12-02 液体火箭发动机冲击载荷结构响应预示方法
CN202011400057.2 2020-12-02
CN202011400048.3A CN112504121B (zh) 2020-12-02 2020-12-02 一种大推力火箭发动机结构姿态分析方法
CN202011400048.3 2020-12-02

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CN115200879A (zh) * 2022-09-19 2022-10-18 北京星河动力装备科技有限公司 液体火箭发动机的高空飞行试车关机控制方法及***
CN115879381A (zh) * 2023-03-01 2023-03-31 西安航天动力研究所 一种火箭发动机冲击载荷预测方法、装置、设备及介质
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CN115200879A (zh) * 2022-09-19 2022-10-18 北京星河动力装备科技有限公司 液体火箭发动机的高空飞行试车关机控制方法及***
CN115879381A (zh) * 2023-03-01 2023-03-31 西安航天动力研究所 一种火箭发动机冲击载荷预测方法、装置、设备及介质
CN115879381B (zh) * 2023-03-01 2023-07-14 西安航天动力研究所 一种火箭发动机冲击载荷预测方法、装置、设备及介质
CN115982863A (zh) * 2023-03-16 2023-04-18 西安航天动力研究所 一种控制响应的冲击试验仿真方法、装置、设备及介质
CN116822378A (zh) * 2023-08-25 2023-09-29 中国人民解放军陆军装甲兵学院 基于回归分析的活性芯体弹靶碰撞效应预测方法
CN116822378B (zh) * 2023-08-25 2023-12-08 中国人民解放军陆军装甲兵学院 基于回归分析的活性芯体弹靶碰撞效应预测方法

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